Turbine of internal combustor

ABSTRACT

A turbine of internal combustor includes a first tube and a second tube each containing a shaft stay to receive axial installation of two sides of the turbine blade shaft with two bearings so to secure the assembly of the turbine blade at where between two tubes, thus to prevent the turbine blade from falling off during revolution at high speed; and elastic members are disposed to the stays to produce floating elasticity when the bearings are turning around, thus to protect the shaft and bearing from being vulnerable to damage.

BACKGROUND OF THE INVENTION

(a) Field of the Invention

The present invention is related to a turbine of internal combustor, and more particularly, to one protects shaft and bearing from being vulnerable to damage by preventing runner blades of the turbine from falling off during revolving at high speed.

(b) Description of the Prior Art

Usually an internal combustor operates on the cycle comprised of four steps, respectively in the sequence of air intake→compression→explosion→exhaust. In the course of air intake, an air manifold 12 is connected to an air filter 13 at the air inlet of the internal combustor 11 as illustrated in FIG. 1 of the accompanying drawings. Accordingly, when the internal combustor 11 is operating, the inside of a cylinder is vacuumed after the stroke of explosion completed by the internal combustor 11, the air inlet manifold 12 will actively suck in the ambient air. The air is then filtered into fresh air through the air filter 13 and delivered into through the air inlet manifold 12 to get mixed with gasified fuel in the internal combustor 11 to force out exhaust produced in the cylinder after explosion out of the internal combustor 11. Finally, fresh fuel gas replaces the exhaust for the internal combustor 11 to undergo explosion once again to produce power. This is a general description of the air intake and exhaust processes of the internal combustor 11 of the prior art.

As illustrated in FIGS. 2 and 3, a turbine 2 is usually added to the air inlet manifold 12. A tube 21 is disposed to the turbine 2 and a turbine blade 23 is axially provided with a bearing 22 in the center of the tube 21. One end of the tube 21 relates to air inlet that sucks in the air and faces toward the air filter 13 while the other end relates to an air out to export air flow and faces toward the internal combustor 11. Accordingly, the turning of the turbine blade 23 increases the speed and pressure of the airflow imported into the internal combustor 11.

However, the turbine blade 23 is inserted into the bearing 22 in a bearing jacket 211 of the tube with the end of its shaft 231, and it solely relies upon one end of the axial 231 (i.e., the air inlet to the turbine blade) to define its axial positioning to the tube 21. Furthermore, there is the absence of any locking structure available at the air outlet of the turbine blade 23. Therefore, when the turbine blade 23 revolves at high speed, it can easily fall off. Whereas the end of the axial is directly inserted into the bearing 22, normal tear and wear take place at where between the shaft 231 and the bearing 22 to damage both of the shaft 231 and the bearing 22.

SUMMARY OF THE INVENTION

The primary purpose of the present invention is to provide a turbine of internal combustor that prevents turbine blade revolving at high speed from falling off and protects the shaft and the bearing from being damaged.

To achieve the purpose, the turbine is installed to the air inlet to increase the speed and pressure of the airflow imported into the internal combustor. Wherein, the turbine includes a first tube and a second tube assembled to each other by means of a locking device; and a turbine blade is sandwiched between both tubes. A shaft stay is each disposed to the first and the second tubes. Both sides of the axial of the turbine blade are respectively and axially disposed to their corresponding shaft stays by means of two bearings for both shaft stays to secure the turbine blade assembly to where between the first and the second tubes. Accordingly, the turbine blade while revolving at high speed is prevented from falling off. An elastic member is disposed in the shaft stay to produce floating elasticity when the bearing is turning to protect both of the bearing and the axial from damage.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic view showing an operating status of air inlet of a general internal combustor.

FIG. 2 is a schematic view showing an operating status of a turbine installed in the general internal combustor.

FIG. 3 is a perspective view showing a construction of a turbine of the prior art.

FIG. 4 is an exploded view showing a construction of the turbine of the present invention.

FIG. 5 is a schematic view showing the construction of the turbine of the present invention.

FIG. 6 is an exploded view showing another construction of the turbine of the present invention.

FIG. 7 is a schematic view showing another construction of the turbine of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

Same as the prior art, the turbine of the internal combustor of the present invention is installed at the air inlet manifold of the internal combustor; one end of the turbine relates to an air inlet that sucks in the air and is disposed facing an air filter while another end relates to an air outlet to export airflow and is disposed facing toward the internal combustor to increase speed and pressure of the airflow imported into the internal combustor as the turbine blade revolves.

In the present invention, a turbine 3 includes a first tube 31 and a second tube 32 assembled to each other by a locking means as illustrated in FIGS. 4 and 5. The locking means may be related to an inner thread 41 and an outer thread 42 respectively disposed to the first and the second tubes 31, 32. A turbine blade 33 is sandwiched between the first and the second tubes 31, 32. Each of both of the first and the second tubes 31, 32 is disposed with a shaft stay 34, and each shaft stay 34 is secured by means of multiple ribs 35 in the first and the second tubes 31, 32. A bearing 36 and an elastic member 37 are disposed in the shaft stay 34 for each of both sides of the axial 331 of the turbine blade 33 to be axially disposed in the shaft stays 34 by means of the bearing 36. Meanwhile, the elastic member 37 resiliently pushes against the bearing 36 in the shaft stay 34 and the elastic member 37 may be made in the form of an elastic plate as illustrated in FIG. 4 or FIG. 5.

Both sides of the axial 331 of the turbine blade are axially disposed in both shaft stays 34 by means of two bearings 36 to allow both shaft stays 34 to secure the assembly of the turbine blade 33 at where between the first and the second tubes to prevent the turbine blade 33 revolving at high speed from falling off. The elastic member 37 provided in the shaft stay produces floating elasticity for the active bearing to protect the axial and the bearing from being damaged.

Furthermore, as illustrated in FIG. 6 for another preferred embodiment of the locking device for the present invention, the locking device relates to a set of locking slot 43 and a locking member 44 respectively provided to the first and the second tubes 31, 32. The opening of the locking slot 44 is located at the top of the first tube 31 to receive the locking member 43 and slide in a given direction for the locking member 43 to be locked into the locking slot 44. As illustrated in FIG. 7, at the same time the assembly of the first and the second tubes 31, 32 is secured in place, both sides of the turbine blade 33 are sealed.

The prevent invention provides an improved structure of a turbine of an internal combustor, and the application for a utility patent is duly filed accordingly. However, it is to be noted that the preferred embodiments disclosed in the specification and the accompanying drawings are not limiting the present invention; and that any construction, installation, or characteristics that is same or similar to that of the present invention should fall within the scope of the purposes and claims of the present invention. 

1. A turbine of an internal combustor installed at air inlet of the internal combustor to increase speed and pressure of the air imported into the internal combustor includes a first tube and a second tube assembled to each other by a locking means; a turbine blade being disposed at where between two tubes; a shaft stay being provided to each of both of the first and the second tubes; both sides of the turbine blade being axially disposed in their corresponding shaft stay by means of a bearing; and an elastic member being provided in the stay to produce floating elasticity when the bearing turns.
 2. A turbine of an internal combustor of claim 1, wherein the locking device for the first tube and the second tube is comprised of an inner thread and an outer thread.
 3. A turbine of an internal combustor of claim 1, wherein the locking device for the first tube and the second tube is comprised of a locking member and a locking slot.
 4. A turbine of an internal combustor of claim 1, wherein the turbine blade is axially disposed in the bearing by means of the rolling shaft.
 5. A turbine of an internal combustor of claim 1, wherein the elastic member is related to an elastic plate.
 6. A turbine of an internal combustor of claim 1, wherein each stay is secured in place respectively in the first tube and the second tube by means of multiple ribs. 